Note: Descriptions are shown in the official language in which they were submitted.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
1
LAUNCH APPAtPiTUS
The invention relates to a launch apparatus.
In numerous civilian applications devices are used that are
suitable for the launch of different types of projectile into
the sky.
These projectiles are constructed for the purpose for which
they are to be used and have dimensions that differ from one
another: the devices arranged for their launch must, therefore,
also have dimensions and mechanical structures that are
different from one another and such as to adapt to the type of
projectile to be launched. A known launch device comprises one
or more pipes or mortar tubes, inside which a respective
projectile is placed to be launched.
Each projectile consists of a shell that contains the material
to be launched, of a charge of launch powders made up together
with the shell in a wrapping that is normally of paper.
The launch of a projectile occurs by igniting the charge of
launch powders that explode and thus supply the propulsive
force for the shell; ignition of the launch powders occurs by
means of electric igniters actuated by a command.
Each electric igniter comprises a tubular body at an end of
which a head for ignition by incandescence is provided that is
supplied with a pair of wires that extends inside and beyond
the tubular body for a suitable length to reach a power plant
provided with pairs of connecting terminals.
The ignition head of the electric igniter is generally inserted
directly into the charge of launch powders of a projectile
during assembly of- the latter or it is connected to a fuse
that, in turn, is inserted into the charge of launch powders
already during assembly of the projectile.
When the igniter receives an electric pulse from the command
power plant, the ignition head ignites, directly igniting in
the first case the launch powders and in the second case the
fuse, which in turn ignites the latter.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
2
Known launch devices generally comprise a great number of
launch tubes that are combined together, whether they are used
for example to remove birds from a zone in which they cannot be
or to launch fireworks.
An example of zones in which birds cannot be, are airports
because, as is known, if birds are accidentally sucked up
inside the engines of aircraft, especially when the latter are
subjected to maximum stress during the take-off phase, the
engines may suddenly lose power and the aeroplane may risk
having to abort the task or even risk falling to the ground.
For this reason, removal of the birds is currently achieved by
arranging along the runways a great number of launch devices,
each one of which comprises a significant number of launch
pipes inside which projectiles are placed that have shells
loaded with explosive materials so that, when they are launched
into the sky, the igniting launch powders raise the shells to a
preset height and then explode, detonated by a fuse provided
for that purpose, producing a loud noise or a coloured and very
bright cloud of smoke: in both cases the birds are frightened
and are made to move away from the area.
Owing to the natural instinct of the birds to return to their
previously chosen haunts as soon as the brief effect of the
detonation has ceased, or the cloud of smoke has scattered, to
keep these zones clear, it is indispensable to launch
projectiles at a certain frequency, cyclically reloading the
launch devices.
When the latter are used in the pyrotechnic sector, they must
be able both to launch a high number of projectiles to obtain
the desired effects and to make the launches according to
preset time sequences and intervals, for example to follow the
rhythm of a preset musical accompaniment that accompanies a
fireworks show.
Furthermore, the launch devices must be secure, both when they
are used and when they are transported.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
3
Currently, the preparation, positioning and activation of the
launch devices require the intervention of a considerable
number of operators who have to load the projectiles into the
launch devices and connect the latter with the power plants,
which are provided with terminals connecting each pair of wires
to each electric igniter.
The power plant is, in turn, connected to a control apparatus
that is manoeuvrable by an operator, by operating which the
launches of the projectiles of each launch apparatus are
actuated.
Actuation of the launch devices thus requires the drawing up
and positioning of a large number of electric wires.
This state of the art has certain drawbacks.
A first drawback is that when the launch devices are numerous
to cover a vast operating zone from which it is necessary to
remove birds, the mass of electric wires to handle and to
arrange for the connections between the igniters and the power
plants becomes significant and requires, as already said, the
intervention or more than one operator assigned to this work:
this adversely affects the total costs of use of the known
launch devices.
Another drawback is that the launch devices are generally
placed over long distances, reaching, in the case of take-off
and landing runways of airports, several kilometres: the
lengths of connecting wires are therefore proportionally great
and their positioning requires fatiguing and repeated
displacements of operators between the power plants and the
different launch devices.
Another drawback is that if the number of wires necessary for
the connections between the electric igniters and the control
panels is high, and if the distances to be covered are
significant, the cost of the igniters and of the wires becomes
noticeable.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
4
Another drawback is that known launch devices are constructed,
as said previously, with specific structural features, that are
determined by the uses for which they are intended and are not
able to launch projectiles that are different from those for
which they were constructed.
For example, with a launch device designed to launch
projectiles arranged to dissuade birds, it is not possible to
launch projectiles for pyrotechnical use or for launching
confetti and vice versa.
A further drawback is that known launch devices do not enable
it to be ascertained with certainty whether the launch of a
projectile occurred correctly without proceeding to a direct
inspection of the launch device, with serious danger for those
performing this operation if a projectile has remained inside a
launch device although the launch command has been given.
Another drawback is that by using known launch devices, it is
very difficult to make planned launch sequences because in
order to obtain these sequences it is necessary to set up power
plants equipped with a large number of pairs of terminals for
attaching all the terminal ends of numerous pairs of wires that
come from all the igniters of all the launch devices used.
Another drawback is that in order to be able to be launched
with known launch devices, the projectiles have to be prepared
in a complete manner and already ready to be launched, i.e.
with the electric igniters or with the fuses connected to the
electric igniters already inserted in the launch charges of the
projectiles; therefore, transport of the latter from the
factories to the places of use is very dangerous because the
electric igniters may sometimes, in the presence of particular
climatic factors, spontaneously ignite, causing sudden and
devastating explosions that cause the demolition of structures
and the injury and death of operators.
The object of the invention is to improve the state of the art.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
An object of the invention is to make a launch apparatus that
is usable for many uses without requiring any structural
adaptation.
Another object of the invention is to make a launch apparatus
5 that does not require connections by means of wires between
projectiles and power plants.
A further object of the invention is to make a launch apparatus
that enables launches to be made according to preset or
presettable sequences.
A further object of the invention is to make a launch apparatus
that enables it to be ascertained easily and without risk to
operators whether the launch of a projectile has occurred
correctly.
Another object of the invention is to make a launch apparatus
that enables it to be remotely actuated, individually or with
other models of the same type, using a single control unit,
e.g. a computer.
Another object of the invention is to make a launch apparatus
that can operate with projectiles that are actuatable only at
the moment of the launch, whilst during their assembly and
transport, they can remain substantially inert, considerably
increasing the safety of operators.
According to an aspect of the invention there is provided an
apparatus, comprising: loading means for loading projectiles
for civilian use, in particular for fireworks displays, to be
launched by propellant means, characterised in that
communicating with said loading means there is provided housing
means for receiving capsule means containing actuating means of
said propellant means.
The apparatus thus enables projectiles intended for civilian
and different use to be launched with a single apparatus
following, when required, preset launch sequences; the
apparatus furthermore enables projectiles to be launched for
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
6
civilian use to be transported that are substantially inert
until the moment of launch.
The apparatus can furthermore be remote-controlled without
cable connections having to be made by electric igniters and
connecting power plants.
Further features and advantages will become clearer from the
disclosure of an embodiment of an apparatus, illustrated by way
of non-limitative example, in the attached tables of drawings
in which:
Figure 1 is a schematic longitudinal section view of an
apparatus for launching projectiles for civilian use, taken
along a plane I-I in Figure 4;
Figure 2 is a fragmentary view on an enlarged scale of a detail
of the launch apparatus;
Figure 3 is a fragmentary schematic view of an enlarged detail
of the launch apparatus in Figure 1 and in which signal
emitting means are visible;
Figure 4 is a schematic view from above of the launch apparatus
in Figure 1;
Figure 5 is a schematic longitudinal section view of a launch
apparatus, taken along a plane I-I of Figure 4 in a second
possible embodiment;
Figure 6 shows a fragmentary view of a launch apparatus placed
in a tilted position;
Figure 7 is a perspective view of a launch apparatus in a third
possible embodiment;
Figure 8 is a fragmentary view of a vertical section of the
launch device in Figure 7, taken along a plane VIII-VIII;
Figure 9 is a vertical section view of a fourth possible
embodiment of a launch apparatus;
Figure 10 is fragmentary transverse section view of an upper
portion of the launch apparatus in Figure 9, taken along a
plane X-X.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
7
With particular reference to Figure 1, 1 indicates a launch
apparatus that comprises a series of mortar bodies 6 for
containing projectiles 2 to be launched.
The latter comprise a shell 308b and a base in which a volume
308a of launch powder is contained.
The mortar bodies 6 define an internal chamber 7 that has
smooth walls and which are normally parallel to one another, a
bottom 307 and an opposite open first end 107; in the proximity
of the bottom 307 there is arranged an explosive capsule 9,
known hereinafter as "capsule" 9 for the sake of brevity, which
is housed in a hollow seat 40 that, in the embodiment of the
launch apparatus illustrated in Figures 1 to 6, is obtained in
the bottom 307, in a substantially centred position thereof.
The capsule 9 is actuatable by means of a striker member 13
that is mounted slidable on the inside of a solenoid 114; the
latter is positioned axially aligned on the corresponding
hollow seat 40 and is supported in this position, as will be
better disclosed below.
If required by particular launch needs, also an additional
layer 308 of launch powder can be placed between the explosive
capsule 9 and the projectile 2.
The solenoid 114 is actuatable by means of signals coming from
a wireless emitter 309 and received by a command element 15
comprising, for example, an electronic card 115 connected to
the latter; as visible in Figure 3, the emitter 309 can be
controlled by a device that is in itself known, such as, for
example, computer "C" or a camera "T" or also a photocell "F",
to emit signals that are received by the solenoid 114, which
creates a magnetic field such as to move the striker member 13
to the capsule 9 to hit it and make it explode.
As is also visible in Figure 3, the striker member 13, when it
moves towards the capsule 9 to hit it, axially crosses the
solenoid 114 and is contrasted in its movement by an elastic
return spring 313 that is interposed between the solenoid 114
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
8
and an abutment 314 mounted on the striker member 13; in the
case illustrated, the spring 313 is wound around an end of the
striker member 13, turned in an opposite direction to the
capsule 9.
The launch apparatus 1 may be fitted, together with other
identical parts, as shown in Figure 1, on a box frame 3 that
has a substantially parallelepipedon shape and which has side
walls 22 and a lower wall 23 and is closed at the top by a
plate 30.
Between the plate 30 and the lower wall 23 there is arranged an
intermediate wall 103 on which all the solenoids 114 are
constrained, which are in turn connected to the electronic card
115; the intermediate wall 103 has passage openings 24 at each
of the latter to enable the passage of each respective striker
member 13.
Each mortar body 6 is constrained on the plate 30 with
constraining means that comprises an opening 4 obtained in the
plate 30 and equipped, for example, with an internal thread 5
and with a further thread obtained perimeterally on the outside
of the mortar body 6 at the bottom 307 in such a way as to make
the latter screwable into the respective opening 4 and,
connected to the plate 30.
According to an alternative embodiment, the constraint means
may comprise a bayonet fitting, not illustrated in the drawings
because known to those skilled in the art, interposed between
the bottom 307 and the respective opening 4 in which a mortar
body 6 has to be inserted and fixed.
According to a further embodiment, which is also not shown
because known to those skilled in the art, the constraint means
may comprise a snap fitting, placed between the bottom 307 and
the respective opening 4.
Between the plate 30 and the intermediate wall 103 there is
provided a flat element 10 designed to run on a lower face 118
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
9
of the plate 30 facing the intermediate wall 103 and supported
on the latter by brackets 25.
This flat element 10 is slidable in relation to the plate 30
and is provided with small through holes 26 and with larger
through holes 126 that are alternatively alignable or
misalignable with the hollow seats 40, in such a way as to open
or close them partially, or if required, completely: in this
case none of the small through holes 26 or large through holes
126 is aligned on the hollow seats 40.
The small holes 26 have smaller dimensions than the dimensions
of the capsules 9 whereas the large holes 126 have greater
dimensions than those of the capsules 9.
As the through holes 26 have dimensions such as to be
noticeably smaller than the capsules 9, even when they are
aligned on the hollow seats 40, they enable both the support of
the capsules 9 on the edges that delimit them, retaining them
therein and the passage of the tips of the respective striker
members 13.
The plate 30 is hinged with hinges 27 on one of the side walls
22 of the box frame 3 to enable its rotation and therefore
access to the inside of the latter for the operations of
loading of the capsule 9 into the respective hollow seats 40.
According to another embodiment of the launch device 1,
illustrated in Figures 1 and 2, each bottom 307 forms a raised
shank 8 that extends to the respective opening 4; the shank 8
is threaded on the perimeter with a thread 105 that is
screwable into the latter and is axially crossed by a passage
211.
In this case, the seat 40 in which the capsule 9 is placed is
obtained inside the shank 8, coaxially with the passage 211.
Each first end 107 is closable after a projectile 2 to be
launched has been inserted through the first end 107 into the
respective mortar body 6, with a removable cap 28 that is
dragged away when the projectile 2 is launched.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
According to the embodiment of the launch apparatus 1
illustrated in Figure 1, each solenoid 114 is connected to a
capacitor 29, which is in turn connected to the electronic card
115; by means of the latter nearly all the capacitors 29 are
5 loaded and actuated in such a way as to supply the pulses to
the solenoids 114 according to set sequences, for example from
a launch execution programme installed in a computer "C".
According to a further embodiment of the launch apparatus 1
illustrated in Figure 6, which is usable to launch in tilted
10 directions the projectiles 2 to be launched, the shank 8 that
extends from the bottom 307, can be screwed into a seat 41
obtained inside a tilted base 321 that protrudes above the
plate 30.
In the embodiment of the launch apparatus 1 illustrated in
Figure 7, the opening 4 is obtained directly in the plate 30.
The opening 4 has a third open end 104 and a fourth open end
204, opposite said third end 104.
On the third open end 104, a mortar body 6 is fittable and
fixable, for example by means of a thread 5.
The mortar body 6 is equipped, on the face of the bottom 307
facing the opening 4, with the shank 8 threaded externally to
screw into the third end 104 of the opening 4 by means of the
thread 5.
In the embodiment of the launch apparatus illustrated in Figure
7, the plate 30 is mounted slidably in the frame 3 on suitable
guides 150 and in it there is obtained, as an extension of the
opening 4, but on the opposite side to the plate 30,
substantially corresponding coaxially with the opening 4, a
hollow seat 40 inside which the capsule 9 is insertable.
Immediately below the plate 30, the flat element 10 is slidably
mounted that, also in this case, can slide in substantial
contact with the lower face 118 of the plate 30 and which at
the hollow seat 40, is traversed by a large through hole 126
that, when the flat element 10 is completely inserted into the
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
11
frame 3, is substantially aligned to the hollow seat 40, or
slightly out of alignment in relation to the latter.
Also the plate 30, like the flat element 10, is slidable along
the frame 3: when both are slid to the outside of the frame 3
to be extracted, the hollow seat 40 is made accessible from
outside to load or substitute the capsule 9.
The flat element 10 is in turn slidable in relation to the
plate 30 and, as said before, when it is inserted completely
into the frame 3, the hollow seat 40 is slightly misaligned in
relation to the large through hole 126: in this way, a part of
the perimeter edge that delimits it, provides a support and
retaining lip for the base of the capsule 9, albeit without
completely closing the passage between the hollow seat 40 and
the large hole 126, so as to enable the striker member 13, when
it is actuated, to reach the capsule 9.
Between the plate 30 and the flat element 10 there is provided
an element 20 for locking reciprocal sliding.
The element 20 comprises a key 16 that is fittable in
corresponding holes 17 and 19 obtained respectively in the
plate 30 of the frame 3 and in the flat element 10, when the
holes 17 and 19 are in a configuration aligned vertically on
one another.
In another embodiment of the launch apparatus 1 illustrated in
Figures 9 and 10,'the launch apparatus 1 comprises a box-shaped
frame 3, which is formed by an upper wall 3a traversed by at
least a window 203, by side walls 22 and by a lower wall 23.
The upper wall 3a is removable or simply openable as indicated
by the arrow A to access the inside of the box frame 3.
Inside the latter there is mounted on supports 205 an
intermediate wall 103, which is parallel to the upper wall 3a
and which supports, substantially centred, a vertical shaft 206
rotatably driven by a motor unit 207, the latter also is
supported on the intermediate wall 103, for example by means of
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
12
brackets 208; the motor unit 207 is of the type with indexed
rotation, according to angles of a preset amplitude.
Onto the shaft 206 there is fitted with gap and in such a way
as to pass through a central opening 18 a circular plate 30
that is rotatingly supported on a flat element 10, which is
also circular in shape, parallel to it, that is splined on the
shaft 206 and which is fixed to it by means of a screwed knob
223 so as to rotate with it.
The flat element 10 is affected by a series of large through
holes 126 that are arranged according to a circular
distribution that has a first radius of preset length; in the
plate 30 corresponding hollow seats 40 are obtained, these also
being arranged according to a circular distribution, having a
second radius with a preset length and which is substantially
the same as that of the first radius, in such a way as to be
able to align the hollow seats 40 on the large through holes
126: both the latter and the hollow seats 40 are obtained
spaced apart at equal distribution distances.
The intermediate wall 103 supports in an eccentric position,
and more precisely at a vertical position of the large through
holes 126 and of the hollow seats 40, a striker member 13 that
is actuated with a solenoid 114; this is actuatable by means of
a control element, indicated by 15, which pulses reach from an
external wireless-type emitting device 309 which can be
connected, for example to a camera, or to a remote control, or
via cable to a switch or to other devices that are not shown
because they are known to those skilled in the art.
In each hollow seat 40 a capsule 9 containing explosive
material is insertable; on the top end of each hollow seat 40
there is defined an opening 4 equipped with internal threading
5 in which a shank 8 is screwable that extends raised from a
bottom 307 of a corresponding mortar body 6, which defines,
inside itself, an internal cavity 7 that has, as in the
previously disclosed embodiments, smooth walls and which is
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
13
suitable for receiving a projectile 2 to launch that is loaded
through a first open end 107 of the mortar body 6.
The shank 8 is axially traversed by a gap 221 that connects the
internal cavity 7 to the respective hollow seat 40.
It should be noted that the flat element 10, being supported on
the plate 30, for example by means of bracket elements 230, is
rotatingly driven simultaneously to the latter by the motor
unit 207: nevertheless, the flat element 10 is also rotatable
by a few degrees in relation to the plate 30, as shown in
detail in figure 3, so that the edges of the hollow seats 40 of
the flat element 10 provide the capsules 9 with a sort of
segment support lip 222 to prevent the latter falling out of
the respective hollow seats 40.
The operation of the launch apparatus in the embodiment
illustrated in Figures 1 to 6 is as follows: one or more launch
apparatuses 1 mounted on respective support frames 3 are
located in preset zones to carry out the launches.
In the case of pyrotechnic use, it is important to note that
the projectiles, 2 to be launched can be conveyed before the
launches with relative security, it not being necessary to make
assemble them providing conventional electric igniters already
mounted inside them: in fact, the explosive action is provided
by the caps 9 only when they are hit by the respective striker
members 13.
In order to load the explosive capsules 9 into the respective
first hollow seats 40, an operator rotates the plate 30 in such
a way as to be able to access the inside of the box frame 3; on
the plate 30 a preset number of mortar bodies 6 is constrained,
for example by screwing the shanks 8 into the respective
openings 4.
When the plate 30 is rotated in relation to the frame 3, the
operator slides the flat element 10 along the face 118, until
the larger through holes 126 of the latter are aligned on the
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
14
first hollow seats 40: in this position, the operator can
insert the explosive capsules 9 into them.
He then slides the flat element 10 in such a way as to align
the smaller through holes 26 on the first hollow seats 40 or,
if the launches do not have to be carried out within a short
time and it is therefore necessary to keep both the launch
apparatuses 1 secure, slides the flat element 10 in such a way
as to keep both the small through holes 26 and the large
through holes 126 misaligned in relation to the first hollow
seats 40, i.e. in such a way that the full body of th.e flat
element 10 shuts it, thus preventing accidental percussion
actions of the striker members 13 on the capsules 9.
The operator, after completing loading of the capsules 9 into
the respective first hollow seats 40, recloses the plate 30
and, in order to arrange the launch apparatuses 1 for
launching, slides the flat element 10 by for example acting on
pickup handles provided precisely for the purpose protruding
from the latter, in such a way as to align only the small
through holes 26 on the first hollow seats 40.
In this configuration, the capsules 9 are retained inside the
respective first hollow seats 40 as, the small through seats 26
being smaller than the capsules 9, the latter rest on the edges
of the small through holes 26 without traversing them;
simultaneously, the passage remains open for the striker
members 13 through the small though holes 26.
The operator then proceeds to place inside each mortar body 6
the corresponding projectile 2 to be launched through the first
end 107, then reclosing it with the cover 28.
The operator can then move away from the launch apparatuses 1
that are ready to launch the projectiles 2 and goes to a safety
zone far from them, in which a control device is arranged, for
example a computer "C", and activates therewith the remote
signal emitter 309; these signals are received by the
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
electronic card 115 and from the latter they are transmitted to
the single solenoids 114.
The striker members 13 are made to perform a capsule 9
percussion stroke by the magnetic fields generated by the
5 solenoids 114; the percussion stroke occurs by overcoming the
contrast action of the contrast springs 313.
When a striker member 13 knocks against a corresponding capsule
9, said striker member 13 causes said capsule 9 to explode
without any connection with wires being necessary; the
10 explosion ignites the propellant powders that are normally
inserted inside the projectile 2 to be launched during their
assembly; the corresponding projectile is then launched to the
sky through the first end 107, dragging with it the respective
cover 28.
15 The absence of the latter from a first end 107 of a mortar body
6 thus clearly indicates to the operators, and without the need
for them to move dangerously near it, that a launch has
occurred correctly and that there is no unexploded projectile 2
in it.
It is to be pointed out that it is possible to programme the
signals to the different solenoids 114 that make up one or more
launch apparatuses 1, in such a way that they actuate launches
with preset sequences in order to be able to follow programmed
patterns or schedules.
If the features of a projectile 2 to be launched are such as to
require an increase of the propulsive thrust, for example when
it is very heavy, it is possible to interpose in the internal
chamber 7, between the projectile 2 and the bottom 307, a layer
308 of launch powder that is ignited when the corresponding
capsule 9 explodes, increasing the action of the launch powders
normally inserted inside the projectiles 2.
The remote signal emitter 309, in another form of use of the
launch apparatus 1, for example for removing birds, can be a
camera "T" which, when it detects the presence of birds in a
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
16
zone to be protected, automatically actuates the emitter 309,
which in turn actuates one or more of the solenoids 114,
actuating the corresponding striker members 13 and causing the
launch of one or more projectiles 2.
Similarly, the camera "T" can be replaced by a photocell "F" or
by another device that is in itself known.
It should be noted that in order to arrange and maintain in a
correct position the projectiles 2 to be launched in the
internal chambers 7, the perimeter walls of the latter can be
tilted and converging towards the bottom 307.
The operation of the launch apparatus in the possible
embodiment illustrated in Figures 7 and 8 is as follows: the
capsules 9 are loaded into the respective hollow seats 40 by
extracting from the frame 3 both the plate 30 and the flat
element 10.
In order to load the capsules 9 without their falling, the flat
element 10 is slid in relation to the plate 30 in such a way as
to reciprocally misalign the hollow seats 40 and the large
through holes 126 so as to create with the flat element 10 a
sort of bottom suitable for supporting the caps 9 inside the
respective hollow seats 40.
After loading of the capsules 9 has been completed, both the
plate and the flat element 10 are reinserted inside the frame
3, maintaining the misalignment until the hollow seats 40 are
aligned on the respective striker members 13.
The plate 30 and the flat element 10 are locked in this
position by reinserting the key 16 in the coaxially aligned
holes 17 and 19.
A projectile 2 is then placed in the containing chamber 7 and
when the solenoid 114 is actuated by the control element 15,
i.e. by the electronic card 115, for example by a pulse coming
from a bird-detection element, the striker member 13 hits the
capsule 9, making it explode.
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
17
The propulsive force produced by the explosion of the capsule 9
is projected through the gap 221 and primes the launch powder
usually contained in a projectile 2, igniting it and activating
the thrust that launches the projectile 2 towards the sky.
The projectile 2 is prepared in such a way as to in turn
explode when it reaches a preset height, producing, for
example, a loud noise that frightens the birds that are in the
zone surrounding the launch device 1, scattering them.
Also in this embodiment, if the sole propulsive force supplied
by the capsule 9 is not sufficient to launch a particularly
heavy projectile 2, the launch powder layer is added to the
internal chamber 7 between the projectile 2 and the bottom 307;
when the capsule 9 is exploded, this ignites the layer 308 of
launch powder, which, by exploding, provides an increase in
propulsive force beyond what is provided by the launch powder
present in a projectile 2 to be launched.
Also in this embodiment of the launch apparatus 1 it is
possible to programme the succession of launches of projectiles
2, activating a preset sequence of pulses sent to the various
solenoids 114.
Operation of the embodiment of the launch apparatus 1
illustrated in Figures 9 and 10 is as follows: each mortar body
6 is loaded with projectiles 2 by inserting them into the
internal chambers 7 through the first end 107; the capsules 9
are loaded by opening the top wall 30a and unscrewing the
threaded knob 223; this frees access to the plate 30 and to the
flat element 10 supported on it; both are then extracted from
the box frame 3 and if necessary the capsules 9 that were
already previously fired are first unloaded and subsequently
the new capsules 9 are inserted inside the respective hollow
seats 40; when loading is complete, the plate 30, which has a
circular shape, is rotated in relation to the flat element 10
by an angle. of a few degrees such that the edges of the large
through holes 126 of the flat element 10 provide a sort of base
CA 02564823 2006-10-27
WO 2005/106379 PCT/IB2005/001219
18
support plane 222 that retains the capsules 9 inside the
respective hollow seats 40.
The flat element 10 and the plate 30 are refitted on the shaft
206 and the latter is rotationally locked on the shaft 206 by
tightening the screw knob 223.
The plate 30 and the flat element 10 are connected together by
brackets 230 that enable reciprocal angular rotations of a few
degrees.
The upper closing wall 3a is then reclosed that has the window
203 that is vertically aligned both on one of the mortar bodies
6 and on the striker member 13.
When a pulse is sent to the control means 15, the signal is
sent from the latter that actuates the solenoid 114, which, in
turn, actuates the striker member 13 that hits the capsule 9,
making it explode and causing the launch of the projectile 2
through the through opening 203 towards the sky, as disclosed
for the previous embodiments of the launch apparatus.
By actuating the motor unit 207, which is of the type with
controlled motion, for example indexed rotating, this makes the
plate 30 rotate by an angle suitable for carrying a new mortar
body 6 that is adjacent or at least different from the one
located at the opening 203 and at the striker member 13, from
which the preceding projectile was launched.
A further pulse sent to the control means 15 causes the launch
of a further projectile 2; this sequence is repeated for all
the projectiles contained in the mortar bodies 6.
The rotation steps of the motor unit 207 are programmable and
it is therefore possible to preset the sequence of launches of
projectiles 2, according to specific needs.
Furthermore, if the mortar bodies 6 are devoid of covers 28,
the upper wall 3a protects from inclement weather the
projectiles 2 loaded inside the internal chambers 7 of the
respective mortar bodies 6, except for the projectile 2 that is
aligned on the through opening 203.
